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TASK 05-51-18-200-001
Inspection after Lightning Strike
雷击后检查
WARNING: WEAR AND ATTACH A SAFETY HARNESS WHEN YOU WORK ON
HIGH SECTIONS. A FALL CAN INJURE OR KILL YOU.
警告： 在高空作业时必须有安全保护设施，否则高空坠落可能导致人员伤亡
WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN
POSITION BEFORE YOU START A TASK ON OR NEAR:
- THE FLIGHT CONTROLS
- THE FLIGHT CONTROL SURFACES
THE LANDING GEAR AND THE RELATED DOORS
COMPONENTS THAT MOVE.
警告： 在下列区域工作前必须放置安全装置和警告标示:
- 飞行控制系统
- 飞行操纵面
- 起落架及相关的门
- 会运动的部件
1. Reason for the Job
工作原因
After a lightning strike, before the aircraft continues in service, you must
在雷击之后，在飞机继续运营前,必须完成下列工作
- do a general inspection of the total surface of the aircraft to find the strike areas
-对飞机所有表面进行普查找出雷击区域
- do a careful inspection of the strike areas to find the type and quantity of possible
damage
仔细检查雷击区域来确定可能损伤的类型及数量
-if you find damage, make a decision about the necessary repair/action
如果发现损伤，明确所必须的修理或相关工作
NOTE: To do this inspection, you must have:
- a set of access platforms, 2 m (6.56 ft.) to 11 m (36.1 ft.)
- or an adjustable access platform, 2 m (6.56 ft.) to 11 m (36.1 ft.)
- or a manlift aerial boom, 2 m (6.56 ft.) to 11 m (36.1 ft.)
注意：此类检查所需的设备
-接近平台2M（6.56ft）到11M（36.1ft）
-或可调节高度的接近平台2M（6.56ft）到11M（36.1ft）
-或载人升降平台车高度范围2M（6.56ft）到11M（36.1ft）
2. Job Set-up Information
工作准备信息
A Fixtures, Tools, Test and Support Equipment
工作夹具，测试及辅助工具
REFERENCE
QTY DESIGNATION
No specific
无说明
warning notices
警告牌
No specific
无说明
adjustable access platform 11 m (36 ft. 1 in.)
可调的接近平台车11M（36ft.1in）
B. Referenced Information
参考信息
REFERENCE DESIGNATION
20-28-00-869-002 Table of the Maximum Permitted Resistance Values
23-11-00-710-001 Operational Test of the HF System
23-12-00-710-001 Operational Test of the VHF System
23-12-11-000-001 Removal of the VHF Antennas (4RC1) and (4RC2)
23-12-11-000-002 Removal of the VHF Antenna (4RC3)
23-12-11-000-003 Removal of the VHF COM Antenna
23-28-00-740-001 BITE Test of the Satellite Communication System
23-28-00-740-002 BITE Test of The Satellite Communication System
23-61-00-200-001 - Check Resistance of Tip to Retainer - Check Bonding of Retainer
to Structure
24-22-51-200-001 Check of the Lightning Protection Modules (19XU1, 19XU2)
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the
External Power
25-65-14-000-001 Antenna 112MX (Emergency Locator Transmitter) - Removal
25-65-14-400-001 Antenna 112MX (Emergency Locator Transmitter) - Installation
REFERENCE DESIGNATION
27-14-00-710-001 Operational Test of the Aileron and Hydraulic Actuation
27-14-51-000-001 Removal of the Aileron Servo Control
27-14-51-400-001 Installation of the Aileron Servo Control
27-24-00-710-001 Operational Test of the Rudder Hydraulic Actuation
27-24-51-000-001 Removal of the Rudder Servo Control 1025GM/2025GM/3025GM
27-24-51-400-001 Installation of the Rudder Servo Control 1025GM/2025GM/3025GM
27-34-00-710-001 Operational Test of the Elevator and Hydraulic Actuation
27-34-51-000-001 Removal of the Elevator Servo Control
27-34-51-400-001 Installation of the Elevator Servo Control
27-44-00-710-001 Operational Test of the Jamming Protection Device of the
Trimmable Horizontal Stabilizer Actuator
27-50-00-866-008 Extension of the Flaps on the Ground
27-50-00-866-009 Retraction of the Flaps on the Ground
27-54-00-710-001 Operational Test of the Flap System
27-60-00-866-002 Extension-Retraction of the Spoilers for Maintenance
27-64-00-710-001 Operational Test of the Spoiler Hydraulic Actuation
27-80-00-866-004 Extending the Slats on the Ground
27-80-00-866-005 Retracting the Slats on the Ground
27-84-00-710-001 Operational Test of the Slat System
29-00-00-864-001 Put the Related Hydraulic System in the Depressurized
Configuration before Maintenance Action
30-31-00-710-001 Operational Test of the Probe Ice Protection
30-42-00-710-001 Operational Test of the Windshield Anti-Icing and Defogging
30-71-00-710-001 Operational Test of the Drainmast Ice Protection
32-00-00-481-001 Installation of the Safety Devices on the Landing Gears
32-11-00-200-001 Inspection/Check of the Main Gear
32-12-00-010-001 Open the Main Gear Doors for Access
32-12-00-410-001 Close the Main Gear Doors after Access
32-21-00-200-002 General Visual Inspection of the Nose Landing Gear
32-22-00-010-001 Nose Gear Doors - Ground Doors Opening
32-22-00-410-001 Nose Gear Doors - Ground Doors Closing
32-46-00-740-001 BITE Test of the BSCU
32-69-00-740-001 BITE Check Landing Gear Control Interface Unit (LGCIU) using
MCDU to Ensure that Continuous BITE is Operative
33-41-00-710-001 Operational Test of the Navigation Lights
33-42-00-710-001 Operational Test of the Landing Lights
33-47-00-710-002 Operational Test of the Logo Lights
33-48-00-710-002 Operational Test of the Anti-Collision/Strobe Lighting
33-49-00-710-001 Operational Test of the Wing and Engine Scan Lights
33-51-15-400-001 Installation of the Emergency Overwing Lights 60WL (61WL, 62WL,
63WL)
34-10-00-710-007 Test of the Angle of Attack Warning
34-11-15-200-001 Inspection/Check of the Pitot Probe (9DA1,9DA2,9DA3)
34-11-16-200-001 Inspection of the Static Probe
(7DA1,7DA2,7DA3,8DA1,8DA2,8DA3)
34-11-18-200-002 Inspection/Check of the TAT Sensor (11FP1, 11FP2)
34-11-19-000-001 Removal of the Angle of Attack Sensor (3FP1, 3FP2, 3FP3)
34-11-19-400-001 Installation of the Angle of Attack Sensor (3FP1, 3FP2, 3FP3)
34-13-00-710-001 Operational Test of the AIR DATA Switching Function
34-22-00-710-001 Operational Check of the standby compass including light test and
visual check
34-36-00-710-002 Operational Test of the GPS
34-36-00-710-005 Operational Test of the GPS
34-36-18-000-001 Removal of the Glide/Slope Antenna (4RT)
34-36-18-400-001 Installation of the Glide/Slope Antenna (4RT)
34-41-00-730-001 System Test of the Weather Radar
34-41-00-740-002 BITE Test of the Weather Radar
34-41-11-000-004 Removal of the Weather Radar Antenna Assembly (7SQ,11SQ)
34-41-11-400-005 Installation of the Weather Radar Antenna Assembly (7SQ,11SQ)
34-42-00-740-002 BITE Test of the Radio Altimeter
34-42-11-000-001 Removal of the Radio Altimeter Antennas 5SA1, 5SA2, 6SA1, 6SA2
34-42-11-400-001 Installation of the Radio Altimeter Antennas 5SA1, 5SA2, 6SA1,
6SA2
34-43-00-740-001 BITE Test of the TCAS
34-51-00-710-001 Operational Test of the DME
34-52-00-740-004 BITE Test of the ATC
34-53-00-710-002 Operational Test of the ADF
34-55-00-710-001 Operational Test of the VOR/MKR
34-58-00-710-001 Operational test of the GPS
49-00-00-710-008 Operational Test of the APU (APS 3200)
53-15-11-200-001 Detailed Inspection of the Radome
55-32-11-000-001 Removal of the Vertical Stabilizer Leading-Edge
55-34-11-000-001 Removal of the Vertical Stabilizer Tip
56-11-11-000-001 Removal of the Windshield
56-11-11-200-001 Inspection of the Windshields
56-11-12-000-001 Removal of the Fixed Windows
56-11-12-200-001 Inspection of the Fixed Windows
56-12-11-000-001 Removal of the Sliding Windows
56-12-11-200-001 Inspection of the Sliding Windows
73-21-60-720-040 Functional Test of the Electronic Control Unit (ECU)
73-29-00-710-040 Operational Test of the FADEC on the Ground (with Engine
Motoring)
78-31-00-710-042 Operational Test of the Thrust Reverser System
SRM 31-31-22 Pb 101 (for corrective action)
SRM 51-11-13 (for corrective action)
SRM 52-81-14 Pb 101 (for corrective action)
SRM 52-82-11 Pb 101 (for corrective action)
SRM 53-00-00 Pb 101 (for corrective action)
SRM 53-11-11 Pb 101 (for corrective action)
SRM 53-21-11 Pb 101 (for corrective action)
SRM 53-25-11 Pb 101 (for corrective action)
SRM 53-35-11 Pb 101 (for corrective action)
SRM 55-30-00 Pb 101 (for corrective action)
SRM 55-32-11 Pb 101 (for corrective action)
SRM 55-32-11 PB 101 (for corrective action)
SRM 55-41-00 Pb 101 (for corrective action)
SRM 57-21-11 Pb 101 (for corrective action)
SRM 57-31-21 Pb 101 (for corrective action)
SRM 57-40-00 Pb 101 (for corrective action)
SRM 57-52-00 Pb 101 (for corrective action)
SRM 57-53-00 Pb 101 (for corrective action)
SRM 57-55-11 Pb 101 (for corrective action)
SRM 57-61-21 Pb 101 (for corrective action)
SRM 57-70-00 Pb 101 (for corrective action)
(Ref. Fig. 601/05-51-18-991-001 SHEET 601.1)
(Ref. Fig. 602A/05-51-18-991-002-A SHEET 602A.1)
(Ref. Fig. 602A/05-51-18-991-002-A SHEET 602A.2)
3. Job Set-up
工作准备
A． Not Applicable
不适用
Subtask 05-51-18-210-077
B. General
概述
（1）Lightning
雷击
（a）Lightning always has two or more attachment points (one entry and one exit) on
the aircraft skin.
雷击总是在飞机机体上造成两个或两个以上的雷击点（一个进入点，一个退出点）
（b）Lightning moves back along the surface of the aircraft (swept stroke zone)
between the entry and exit point. This can cause a chain of scattered attachment
points along a line in the direction of travel of the aircraft.
雷击进入点和退出点是沿着飞机（受雷击区域）表面向后移动形成，雷击可能导致
沿飞机飞行方向一连串的雷击点
（c）Lightning hits some areas more frequently than others.
有些区域会比其它区域更频繁遭受雷击
（2）Aircraft zoning
(Ref. Fig. 601/TASK 05-51-18-991-001 SHEET 601.1)
区域划分 (Ref. Fig. 601/TASK 05-51-18-991-001 SHEET 601.1)
（a） The aircraft is divided into three zones related to the probability of lightning
strike:
飞机依据遭受雷击的可能性可以划分为三个区域:
Zone 1
区域 1
- surfaces where there is a high probability of initial lightning attachment (entry or
exit).
这些表面最有可能使雷电在机体上形成附着点（进入或退出）
Zone 2
区域 2
- surfaces where there is a high probability of a "swept stroke zone". The lightning
strike has its initial point of attachment in Zone 1 and moves into Zone 2.
这些表面最有可能使雷击形成连续雷击或多处雷击的情况，雷击进入区域1 后再进
入区域2
Zone 3
区域 3
- this zone includes all of the aircraft surfaces that are not in Zone 1 and 2. In Zone 3
there is a low probability of attachment of a lightning strike. However, high lightning
currents can go through Zone 3 by direct conduction between 2 attachment points.
Zone 3 currents will also go into Zones 1 and 2.
除区域1、2 外的所有表面。区域3 发生雷击的可能性较小，然而,强大的雷击电流
可以在2 个雷击点之间形成直接通路从而进入区域3，同样区域3 的电流也可以进
入区域1 和2.
（b）Zones 1 and 2 are divided into A and B areas related to the probability of continued
attachment of the arc (hang on). The probability of arc hang on is low in A areas
and high in B areas
根据放电电弧的附着可能性又将区域1、2 分成A、B 两个部分。在区域A 形成电弧
的可能性小,在区域B 形成电弧的可能性大
Zone 1A:
区域 1A
- area where there is a high probability of initial attachment and low probability of
arc hang on, such as the forward-mounted pitot probes, the radome diverter strips
and the nacelle leading edges.
该区域具有高的雷击初始附着的可能性,低的形成电弧的可能性,比如迎风安装的皮
托管,雷达罩上的导流条以及吊舱的前缘部分.
Zone 1B
区域 1B
- area where there is a high probability of initial attachment and high probability of
arc hang on, such as the wing, stabilizers and fin tips and some trailing edge areas.
该区域具有高的雷击初始附着的可能性,高的形成电弧的可能性,比如机翼,安定面.翼
尖小翼以及一些后缘区域.
Zone 2A:
区域 2A
- a swept stroke zone with low probability of arc hang on, such as mid-chord
regions of the wing surface, aft of an engine and the total fuselage surface
该区域会形成连续雷击但形成放电电弧的可能性比较小,比如机翼表面中部玄区，发
动机后部以及所有机身表面.
Zone 2B:
区域 2B
- a swept stroke zone with high probability of arc hang on, such as the wing trailing
edge aft of Zone 2A.
该区域会形成连续雷击且形成放电电弧的可能性比较大,比如机翼后缘部分.
（3）Effects on the aircraft structure and systems
对飞机结构和系统的影响.
There are two types of possible risks to the aircraft
有两种对飞机来说可能存在的危险
- indirect effects
间接影响
- direct effects
直接影响
（a） indirect effects
间接影响
Electromagnetic fields
电磁场
- the electromagnetic fields related to the lightning attachment can cause unwanted
transient voltages and currents in the aircraft wiring and systems.
In some conditions (low intensity strike, high protection), the effect on the systems
can be temporary and the systems can operate correctly again after the strike. In
other conditions (low protection, no circuit protection devices), the damage can be
permanent and it will be necessary to replace parts
雷电导致的电磁场可以使飞机的线路和系统产生不必要的瞬变电压和电流。对有些
情况来说（低强度放电，强保护区），对系统的影响是暂时的，系统在雷击之后可
以恢复正常工作。对其他情况来说（弱保护区，没有线路保护装置），遭受损坏是
永久性的，必须更换部件进行修复。
（b）Direct effects
直接影响
The direct effects are the physical damage related to signs such as:
直接影响可以导致如下物理损伤:
1 Pitting/meltthrough
凹陷/击穿
- this is the action of the electrical arc formed when a lightning stroke attaches to the
aircraft (arc root damage at the attachment points or damage caused by current flow
which can appear also far from the attachment points).
该情况是由于飞机在遭受雷击时形成的放电电弧导致的（放电电弧位于雷击附着点或由
于远距附着点的电流造成）
-signs of a lightning attachment are pitting and scorch marks and paint discoloration.
On composite components, in addition to paint discoloration and skin puncturing,
some delamination of the fibers can occur. If there is skin puncturing, there can be
damage to the grounded equipment below composite material fairings.
雷击附着点造成飞机表面凹陷，焦痕或喷漆颜色改变的特征；对于复合材料部件，除了
出现表面穿孔和喷漆颜色改变外，有些化纤材料会出现分层现象。如出现表面破裂情况，
则可能会对复合材料下的接地设备造成损伤.
-you must always compare the damage you find with the limits given in the Structural
Repair Manual (SRM).
对发现的损伤必须与SRM 中所给的限制进行比较 | 
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发表于 2011-8-16 01:13:45
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